Abstract: A gas turbine has a cooling air passage which extends along the leading edge of the blade airfoil, which cooling air passage has an outlet opening which is arranged in the region of the blade tip. The contour of the outlet opening is geometrically similar to the cross section of the cooling air passage. As a result, flow inhomogeneities of the cooling air flow, which locally negatively influence heat transfer, and consequently cooling efficiency, are avoided.

Abstract: A fluid flow machine blade (1) is provided on the outer contour of the airfoil (4) with a thermal barrier coating (41). In this context, quite purposefully, only part-regions of the airfoil have the thermal barrier coating, while well-defined second part-regions of the airfoil (42, 43, 44) are realized purposefully without thermal barrier coating. In particular, along the trailing edge (46) of the airfoil, a region (42) is realized without thermal barrier coating. In further embodiments of the invention, regions of the airfoil (43, 44) which lie adjacent to foot-side (21) or tip (31) platforms of the blades are realized without thermal barrier coating.

Abstract: A gas turbine has a cooling air passage which extends along the leading edge of the blade airfoil, which cooling air passage has an outlet opening which is arranged in the region of the blade tip. The contour of the outlet opening is geometrically similar to the cross section of the cooling air passage. As a result, flow inhomogeneities of the cooling air flow, which locally negatively influence heat transfer, and consequently cooling efficiency, are avoided.

Abstract: A fluid flow machine blade (1) is provided on the outer contour of the airfoil (4) with a thermal barrier coating (41). In this context, quite purposefully, only part-regions of the airfoil have the thermal barrier coating, while well-defined second part-regions of the airfoil (42, 43, 44) are realized purposefully without thermal barrier coating. In particular, along the trailing edge (46) of the airfoil, a region (42) is realized without thermal barrier coating. In further embodiments of the invention, regions of the airfoil (43, 44) which lie adjacent to foot-side (21) or tip (31) platforms of the blades are realized without thermal barrier coating.

Abstract: A gap seal in a gas turbine for sealing off a cooling space, formed between a heat shield and a heat shield carrier, from a hot gas space of the gas turbine. A sealing body is retained in a movable manner on the heat shield, on the one hand, and on a blade carrier, on the other hand, adjacent to the heat shield carrier.

Abstract: The invention relates to a gap seal in a gas turbine for sealing off a cooling space (6), formed between a heat shield (4) and a heat shield carrier (5), from a hot gas space (7) of the gas turbine. A sealing body (10) is retained in a movable manner on the heat shield (4), on the one hand, and on a blade carrier (2), on the other hand, adjacent to the heat shield carrier (5).